Seal system

Abstract

A seal arrangement for a turbo-engine, for sealing a peripheral gap between a rotor and a stator is provided. The stator a seal holder provided with at least one groove for respectively receiving a segmented, dynamic seal. Segments of the dynamic seal are made up of a plurality of brush seal segments, and free ends of bristles of the brush seal segments extend in the radial direction project from the respective groove and lie on the rotor. The or every groove for receiving the brush-type seal segments is designed without an undercut, the brush-type seal segments being received in the respective groove without an undercut in a positive manner.

1. A seal system for a turbo-engine, for sealing a circumferential gap between a rotor and a stator, the stator comprising a seal holder having at least one circumferential groove for receiving a segmented dynamic seal, the segmented dynamic seal including a plurality of segments; each of the segments being brush seal segments having bristles, the bristles having free ends, the free ends of the bristles extending in a radial direction projecting from the at least one groove and resting on the rotor, the at least one groove being a groove without undercut, the brush seal segments being positively secured in the groove;
 wherein the at least one groove includes a plurality of axially spaced circumferential grooves, each receiving a respective one of a plurality of brush seal segments, two adjacent grooves of the plurality of grooves being connected by at least one bore hole extending in an axial direction, the brush seal segments being positively secured in the grooves by clamping elements passing through the bore holes. 
 
     
     
       2. The seal system as recited in  claim 1 ,
 wherein the groove has a uniform axial width, in at least one receptacle section for the brush seal segments, over its entire radial height. 
 
     
     
       3. The seal system as recited in  claim 1 ,
 wherein the bristles of one of the brush seal segments rest axially on a radially longer side wall of the groove, the side wall of the groove forming a support element. 
 
     
     
       4. The seal system as recited in  claim 1 ,
 wherein the clamping elements are pin-type or screw-type clamping elements. 
 
     
     
       5. The seal system as recited in  claim 4 ,
 wherein the or each clamping element is designed as a passing pin or a headless screw. 
 
     
     
       6. The seal system as recited in  claim 1 ,
 wherein the seal holder is segmented such that a plurality of seal holder segments extends over the circumference of the rotor, and together forms a circular ring-shaped seal holder. 
 
     
     
       7. A seal system for a turbo-engine for sealing a gap between two stator-side components comprising a first stator-side component and a second stator-side component, the first stator-side component having at least one groove for receiving a static seal, the static seal being designed as a brush seal having bristles, the bristles having free ends, the free ends of the bristles projecting from the groove and resting on a second stator-side component,
 the groove being a groove without undercut, the brush seal being secured in the groove with a radial clearance; wherein the at least one groove includes a plurality of axially spaced circumferential grooves, each receiving a respective one of a plurality of brush seal segments, two adjacent grooves of the plurality of grooves being connected by at least one bore hole extending in an axial direction, the brush seal segments being positively secured in the grooves by clamping elements passing through the bore holes. 
 
     
     
       8. The seal system as recited in  claim 7 ,
 wherein in a receptacle section for the brush seal, the groove has a uniform radial height over its entire axial width. 
 
     
     
       9. A turbo-engine having at least one seal system as recited in  claim 1 . 
     
     
       10. A gas turbine, an aircraft engine in particular, having at least one seal system as recited in  claim 1 . 
     
     
       11. A steam turbine having at least one seal system as recited in  claim 1 . 
     
     
       12. A turbo-engine having at least one seal system as recited in  claim 7 . 
     
     
       13. A gas turbine, an aircraft engine in particular, having at least one seal system as recited in  claim 7 . 
     
     
       14. A steam turbine having at least one seal system as recited in  claim 7 .